Front engine attachment system for an aircraft engine, having rod systems with two rods
US-11572184-B2 · Feb 7, 2023 · US
Front engine attachment system for an aircraft engine, comprising a more a lightweight structure
US11975856B2 · US · B2
| Field | Value |
|---|---|
| Publication number | US-11975856-B2 |
| Application number | US-202017756554-A |
| Country | US |
| Kind code | B2 |
| Filing date | Nov 16, 2020 |
| Priority date | Nov 27, 2019 |
| Publication date | May 7, 2024 |
| Grant date | May 7, 2024 |
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- Title
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Abstract
Official abstract text for this publication.
A front engine attachment system for an engine of an aircraft. An engine pylon has a frontal rib with a front engine attachment with a first link rod which is fixed directly to the frontal rib by two connecting points. A second link rod is provided which has a first end fixed to the first link rod by a connecting point. The first link rod is fixed directly to an engine casing by at least two connecting points and a second end of the second link rod is fixed to the engine casing by a third connecting point. The first link rod may be made up of two adjoining plates that are fixed together. Also, an aircraft with such a front engine attachment system.
First claim
Opening claim text (preview).
The invention claimed is: 1. A front engine attachment system for an engine of an aircraft, the front engine attachment system comprising: an engine pylon having a frontal rib in a front part, a front engine attachment having a first link rod which is fixed, in an articulated manner, directly to the frontal rib by two connecting points, the first link rod being a monolithic piece and a second link rod having a first end which is fixed in an articulated manner to the first link rod by a connecting point, and an engine casing of the engine, wherein the first link rod is fixed, in an articulated manner, directly to the engine casing by a first connecting point and a second connecting point, the first connecting point is a laterally outermost connecting point between the front engine attachment and the engine casing, wherein a second end of the second link rod is fixed, in an articulated manner, to the engine casing by a third connecting point, wherein the second connecting point is arranged between the first connecting point and the third connecting point, and, wherein a rotational axis of the first link rod relative to the frontal rib passes through the two connecting points between the first link rod and the frontal rib, the rotation axis being horizontal. 2. The front engine attachment system of claim 1 , wherein the first link rod comprises a first plate, the first plate joined to a second plate such that the first and second plates are fixed together. 3. An aircraft having a structure, the engine and the front engine attachment system according to claim 2 , wherein the engine pylon is fixed to the structure, and wherein the engine casing is secured to the engine. 4. An aircraft having a structure, the engine and the front engine attachment system according to claim 1 , wherein the engine pylon is fixed to the structure, and wherein the engine casing is secured to the engine.
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- What does patent US11975856B2 cover?
- A front engine attachment system for an engine of an aircraft. An engine pylon has a frontal rib with a front engine attachment with a first link rod which is fixed directly to the frontal rib by two connecting points. A second link rod is provided which has a first end fixed to the first link rod by a connecting point. The first link rod is fixed directly to an engine casing by at least two co…
- Who is the assignee on this patent?
- Airbus Operations Sas
- What technology area does this patent fall under?
- Primary CPC classification B64D27/18. Mapped technology areas include Operations & Transport.
- When was this patent published?
- Publication date Tue May 07 2024 00:00:00 GMT+0000 (Coordinated Universal Time) (B2). Legal status and post-grant events are not shown on this page.
- What related patents are in patentsdb?
- We list 2 related publications on this page (citations in our corpus or others sharing the same primary CPC).